CN113232852B - Transmission mechanism for tilting rotorcraft wing - Google Patents
Transmission mechanism for tilting rotorcraft wing Download PDFInfo
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- CN113232852B CN113232852B CN202110510359.3A CN202110510359A CN113232852B CN 113232852 B CN113232852 B CN 113232852B CN 202110510359 A CN202110510359 A CN 202110510359A CN 113232852 B CN113232852 B CN 113232852B
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- wing
- speed reducer
- tilting
- nacelle
- rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
- B64C27/605—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The invention provides a transmission mechanism for a tiltrotor aircraft wing. The transmission mechanism comprises a double engine, a left-right primary speed reducer, a main transmission shaft, a middle speed reducer, a left-right tilting structure, a left-right wing transmission shaft and a secondary speed reducer. The output rotation speed of the left and right engines is transmitted to the main transmission shaft through the left and right first-stage speed reducers, and after the speed is increased and split through the middle speed reducer, the power is transmitted to the two-stage speed reducers at the left and right ends through the left and right wing transmission shafts respectively. The tilting structure of the aircraft is arranged on the tilting shaft, and a planetary roller screw is adopted to drive a hinge four-bar mechanism with a composite rocker arm, so that tilting control of the whole rotor nacelle is realized. The aircraft rotor transmission mechanism can realize the installation of main transmission components and the arrangement of the spiral bevel gear steering mechanism in a limited space, and provides effective bearing support and lubrication for each transmission shaft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a transmission mechanism for a wing of a tiltrotor aircraft.
Background
The tilting rotor type aircraft has the advantages of vertical take-off and landing and short take-off and landing, and combines the functions of a traditional helicopter with the remote high-speed cruising function of a vortex propeller aircraft. There is only one type of tiltrotor aircraft in the united states today that is listed as a model in the military aviation product development program in the world. The V22 adopts a two-stage screw rod mechanism driven by a double-head hydraulic motor to drive the rotor to tilt, and the two-stage screw rod mechanism can obtain a larger working stroke in a smaller installation size, so that the V22 can directly drive the rotor to tilt by using the two-stage screw rod. However, the V22C adopts hydraulic pressure as power, so that the problems of heavy structure, complex structure, large space volume and the like are caused.
The rotor drive system provides key power transfer and reversing functions for controlling rotor rotation and tilting. However, the design space of the left wing, the right wing and the rotor nacelle is strictly limited, the installation of a main transmission part and the arrangement of a spiral bevel gear steering mechanism are required to be completed in a narrow space, effective bearing support and lubrication are provided for each transmission shaft, and interfaces and support positions are required to be reserved for a tilting structure, an automatic inclinator and a rotor pitch-changing electric cylinder. Meanwhile, the requirements on speed reduction and vibration are higher, so that the stability of the whole rotor wing in transmission and tilting is ensured, and the design difficulty of a transmission mechanism system is further increased.
Disclosure of Invention
The invention aims to provide a transmission mechanism for a tilting rotorcraft wing, which solves the problems in the prior art.
The technical scheme adopted for achieving the purpose of the invention is that a transmission mechanism for the wing of the tiltrotor aircraft is characterized in that the wing is respectively arranged on the left side and the right side of the body of the tiltrotor aircraft. A rotor nacelle is positioned at the tip of the wing. The body is fixed with a tilting shaft. The tilting shaft serves as a rotating shaft of the rotor nacelle, bears the load generated by the rotor nacelle and transmits the load to the fuselage. The rotor nacelle is responsible for tilting, and the rotor is installed on the rotor nacelle, rotates along with the rotor nacelle, realizes flight mode's conversion. The device comprises a main transmission shaft, a middle speed reducer, a left tilting structure, a right tilting structure, a left wing transmission shaft, a right wing transmission shaft, a left three-stage speed reducer and a right three-stage speed reducer.
The output power of the main transmission shaft is respectively transmitted to the left wing transmission shaft and the right wing transmission shaft after being increased and split by the intermediate speed reducer. The output end of the left wing transmission shaft is provided with a left three-stage speed reducer. The output end of the right wing transmission shaft is provided with a right three-stage speed reducer. The left and right tertiary reducers are disposed in corresponding rotor nacelle.
The left and right camber structures are disposed between the corresponding wing and the rotor nacelle. The left tilting structure and the right tilting structure are identical in structure. The left tilting structure comprises a servo motor, a nacelle auxiliary rocker arm, a wing side auxiliary rocker arm and a planetary roller screw. The planetary roller screw includes a planetary screw nut and a planetary screw. One end of the nacelle auxiliary rocker arm is hinged with a case of the left three-stage speed reducer, and the other end of the nacelle auxiliary rocker arm is hinged with a planetary screw nut. One end of the auxiliary rocker arm on the wing side is hinged with the wing structure, and the other end of the auxiliary rocker arm on the wing side is hinged with the planetary screw nut. The servo motor drives the planetary screw rod to rotate, and the nut on the upper part of the screw rod is pushed to drive the nacelle auxiliary rocker arm and the wing side auxiliary rocker arm to move, so that the left three-stage speed reducer is pushed to rotate around the tilting shaft, and the tilting control of the rotor nacelle is realized.
Further, the engine further comprises a left engine, a right engine, a left-stage speed reducer and a right-stage speed reducer. The output rotating speed of the left engine is transmitted to the main transmission shaft through the left primary speed reducer, and the output rotating speed of the right engine is transmitted to the main transmission shaft through the right primary speed reducer.
Further, the left tilting structure further comprises a flange connection block, a trunnion connection block and a tapered roller bearing.
Further, the servo motor is provided with an electromagnetic braking device. And a photoelectric sensor is arranged on the trunnion connecting block. The planetary screw nut is used as a reflecting surface of the photoelectric sensor, and the motion track and the speed curve of the planetary screw nut can be fed back in the control system. In the working process of the tilting structure, the distance fed back by the photoelectric sensor is converted into speed and then is transmitted to the control system, and the control system compares and analyzes the speed curves of the theoretical and actual planetary screw nuts. When the speed curve exceeds a preset threshold, the control system sends a command to the electromagnetic braking device to conduct power-on or power-off operation, and the electromagnetic braking device conducts braking release or braking operation on the servo motor.
Further, the end face of the wing structure is provided with a limit groove. And limiting pins are arranged on one sides of the nacelle auxiliary rocker arm and the wing side auxiliary rocker arm, which face the wing structure, and the maximum tilting position of the tilting structure is limited through the cooperation of the limiting grooves and the limiting pins.
Further, the left three-stage speed reducer adopts a first-stage spiral bevel gear to reduce the near-end output. The right three-stage speed reducer adopts a first-stage spiral bevel gear to reduce the speed of the far-end output.
Further, the left three-stage speed reducer and the right three-stage speed reducer both adopt the structure form of an axis intersection angle spiral bevel gear speed reducer.
Further, the tilting shaft is hollow, and wire equipment is arranged inside the tilting shaft.
Further, a fairing is arranged between the wing and the rotor nacelle.
The technical effects of the invention are undoubted:
1. the tilting structure realizes a larger tilting angle range of the rotor wing in a limited space, and has the characteristics of small volume and light weight;
2. the tilting structure core execution component adopts a planetary roller screw structure, and the planetary roller screw has higher dynamic load and static load bearing capacity relative to the roller screw, and the threaded tubular column has larger bearing contact area, so that the planetary roller screw has higher impact resistance;
3. the tilting structure relates to an auxiliary rocker arm structure, the auxiliary rocker arm can improve the transmission ratio of the tilting structure, and the tilting structure has the advantage of controlling a large tilting angle in a limited driving stroke. In the whole tilting stroke process of the mechanism, the motion trail of the effective lead screw, the rocker arm, the nut and the servo motor is not interfered with the engine body structure, the nacelle and the wing fairing; when the mechanism moves at the position of 0 degrees to-5 degrees, all tilting structures can be guaranteed to be retracted in the fairing of the joint surface of the nacelle and the wing;
4. the rotor transmission mechanism can realize the installation of main transmission components and the arrangement of the spiral bevel gear steering mechanism in a limited space, and provides effective bearing support and lubrication for each transmission shaft. Meanwhile, the requirements of reserving interfaces and providing supporting positions for the tilting structure, the automatic tilting device and the rotor wing variable-pitch electric cylinder can be met.
Drawings
FIG. 1 is a schematic diagram of a transmission system;
FIG. 2 is a schematic diagram of a tilting structure;
FIG. 3 is a diagram of the positional relationship of the transmission structure;
FIG. 4 is a schematic diagram of a fairing position;
FIG. 5 is a schematic diagram of an intermediate speed reducer;
FIG. 6 is a schematic view of wing mount, wing drive shaft, and tilt structure installation;
fig. 7 is a schematic diagram of a left three stage reduction gear.
In the figure: the left engine 1, the right engine 22, the left primary speed reducer 24, the input stage bevel gear 3, the intermediate drive bevel gear 4, the output bevel gear 2, the main drive shaft 5, the left tertiary speed reducer 6, the driven bevel gear I7, the left tilting structure 9, the intermediate speed reducer 11, the secondary input spiral bevel gear 13, the left output spiral bevel gear 12, the right output spiral bevel gear 14, the right tilting structure 16, the right tertiary speed reducer 19, the driven bevel gear II 18, the servo motor 25, the flange connection block 26, the trunnion connection block 27, the planetary screw nut 28, the nacelle auxiliary rocker arm 29, the planetary screw 31, the tilting shaft 32, the wing side auxiliary rocker arm 33, the tapered roller bearing 34, the photoelectric sensor 35, the left wing shaft 38, and the right wing shaft 39.
Detailed Description
The present invention is further described below with reference to examples, but it should not be construed that the scope of the above subject matter of the present invention is limited to the following examples. Various substitutions and alterations are made according to the ordinary skill and familiar means of the art without departing from the technical spirit of the invention, and all such substitutions and alterations are intended to be included in the scope of the invention.
Example 1:
wings are respectively arranged on the left side and the right side of the tilting rotorcraft body. A rotor nacelle is positioned at the tip of the wing. The body is fixed with a tilting shaft. The tilting shaft serves as a rotating shaft of the rotor nacelle, bears the load generated by the rotor nacelle and transmits the load to the fuselage. The rotor nacelle is responsible for tilting, and the rotor is installed on the rotor nacelle, rotates along with the rotor nacelle, realizes flight mode's conversion.
The present embodiment provides a transmission mechanism for a tiltrotor aircraft wing, including a main drive shaft 5, a middle speed reducer 11, a left tiltrotor structure 9, a right tiltrotor structure 16, a left wing drive shaft 38, a right wing drive shaft 39, a left three-stage speed reducer 6, and a right three-stage speed reducer 19.
The output power of the main transmission shaft 5 is accelerated by the intermediate speed reducer 11 and split, and then is respectively transmitted to the left wing transmission shaft 38 and the right wing transmission shaft 39. The output end of the left wing transmission shaft 38 is provided with a left three-stage speed reducer 6. The output end of the right wing transmission shaft 39 is provided with a right three-stage speed reducer 19. The left 6 and right 19 three-stage retarders are arranged in the corresponding rotor nacelle.
The left and right tilting structures 9, 16 are arranged between the corresponding wing and the nacelle. The left tilting structure 9 and the right tilting structure 16 are identical in structure. The left tilting mechanism 9 includes a servo motor 25, a nacelle auxiliary rocker 29, a wing side auxiliary rocker 33, and a planetary roller screw. The planetary roller screw includes a planetary screw nut 28 and a planetary screw 31. One end of the nacelle auxiliary rocker arm 29 is hinged with the case of the left three-stage speed reducer 6, and the other end is hinged with the planetary screw nut 28. One end of the auxiliary rocker arm 33 on the wing side is hinged with the wing structure, and the other end is hinged with the planetary screw nut 28. The servo motor 25 drives the planetary screw rod 31 to rotate, and the nut 28 on the upper part of the screw rod is pushed to drive the nacelle auxiliary rocker arm 29 and the wing side auxiliary rocker arm 33 to move, so that the left three-stage speed reducer 6 is pushed to rotate around the tilting shaft, and the tilting control of the rotor nacelle is realized.
The pull direction of the rotor system is upward in the vertical take-off and landing state, and the rotor system is tilted to the horizontal forward in the high-speed forward flying state. When the rotor wing of the rotor wing system is vertically upwards, the rotor wing generates lift force, the helicopter can vertically take off, land or hover, and when the operating system changes the posture of the rotor wing to be horizontal, the size of the lift force on the rotor wing and the inclined direction of the lift force of the rotor wing can be changed, so that the aircraft can keep or change the flying state. After taking off, the propulsion device can be rotated to a horizontal position to generate forward thrust, and the propulsion device can fly by relying on wings to generate lift like a fixed-wing propeller plane.
Example 2:
the main structure of this embodiment is the same as that of embodiment 1, and further includes a left engine 1, a right engine 22, a left-stage reduction gear 23, and a right-stage reduction gear 24. The output rotation speed of the left engine 1 is transmitted to the main transmission shaft 5 through the left-stage reducer 23, and the output rotation speed of the right engine 22 is transmitted to the main transmission shaft 5 through the right-stage reducer 24.
Example 3:
the main structure of this embodiment is the same as that of embodiment 1, and the left tilting structure 9 further includes a flange connection block 26, a trunnion connection block 27, and a tapered roller bearing 34. The flange connection block 26 and the tapered roller bearing 34 are mounted on a planetary screw. The outer ring of the tapered roller bearing 34 is engaged with the trunnion connection block 27. The trunnion connection block 27 is connected to the outside. The flange connection block 26 connects the servo motor 25 with the planetary screw 31.
Example 4:
the main structure of this embodiment is the same as that of embodiment 1, and the servo motor 25 has an electromagnetic braking device. A photoelectric sensor 35 is mounted on the trunnion connection block 27. The planetary screw nut 28 serves as a reflecting surface of the photoelectric sensor 35, and the movement track and the speed curve of the planetary screw nut 28 can be fed back in the control system. During the operation of the tilting mechanism, the distance fed back by the photoelectric sensor 35 is converted into a speed and then transmitted to the control system, and the control system compares the speed curves of the theoretical and actual planetary screw nuts 28. When the speed profile exceeds a predetermined threshold, the control system issues a command to the electromagnetic brake device to perform an on-or off-operation, and the electromagnetic brake device performs a brake release or brake operation on the servo motor 25 (servo motor overcurrent protection control).
Example 5:
the main structure of the embodiment is the same as that of embodiment 1, and a limit groove is formed in the end face of the wing structure. The nacelle auxiliary rocker 29 and the wing side auxiliary rocker 33 are provided with limit pins on one side facing the wing structure, and limit the maximum tilting position of the tilting structure through the cooperation of limit grooves and limit pins.
Example 6:
the main structure of the embodiment is the same as that of embodiment 1, and the left three-stage speed reducer 6 adopts a first-stage spiral bevel gear to reduce the output of the near end. The right three-stage speed reducer 19 adopts a first-stage spiral bevel gear to reduce the speed of the distal output. Thereby realizing the reverse contra-rotating function of the left rotor wing and the right rotor wing.
Example 7:
the main structure of the embodiment is the same as that of embodiment 1, and the left three-stage speed reducer 6 and the right three-stage speed reducer 19 both adopt the structure form of an axis intersection angle spiral bevel gear speed reducer.
Example 8:
the main structure of this embodiment is the same as that of embodiment 1, the tilting shaft is hollow, and the electric wire equipment is arranged inside the tilting shaft.
Example 9:
referring to fig. 1 to 7, wings are provided on both left and right sides of a tiltrotor fuselage. A rotor nacelle is positioned at the tip of the wing. The body is fixed with a tilting shaft. The tilting shaft serves as a rotating shaft of the rotor nacelle, bears the load generated by the rotor nacelle and transmits the load to the fuselage. The rotor nacelle is responsible for tilting, and the rotor is installed on the rotor nacelle, rotates along with the rotor nacelle, realizes flight mode's conversion.
The present embodiment provides a transmission mechanism for a tiltrotor aircraft wing, including a left engine 1, a right engine 22, a left primary speed reducer 23, a right primary speed reducer 24, a main transmission shaft 5, an intermediate speed reducer 11, a left tilting structure 9, a right tilting structure 16, a left wing transmission shaft 38, a right wing transmission shaft 39, a left tertiary speed reducer 6, and a right tertiary speed reducer 19.
The output rotation speed of the left engine 1 is transmitted to the main transmission shaft 5 through the left-stage reducer 23, and the output rotation speed of the right engine 22 is transmitted to the main transmission shaft 5 through the right-stage reducer 24.
The left-stage reducer 23 and the right-stage reducer 24 have the same structure. The left stage reducer 24 includes an input stage bevel gear 3, an intermediate drive bevel gear 4, and an output bevel gear 2.
The intermediate speed reducer 10 mainly comprises a three-stage input spiral bevel gear 13, a left output spiral bevel gear 12 and a right output spiral bevel gear 14. The left output spiral bevel gear 12 and the right output spiral bevel gear 14 are simultaneously driven by the input spiral bevel gear 13 to transmit power to the left rotor shaft 38 and the right rotor shaft 39, respectively.
The output rotational speed of the left-hand motor 1 is transmitted to the input bevel gear 3, the input bevel gear 3 and then to the intermediate drive bevel gear 4, and the rotational speed is transmitted to the main drive shaft 5 via the output bevel gear 2. The output rotational speed of the left-hand motor 22 is transmitted to the input bevel gear 21, the input bevel gear 21 and then to the intermediate drive bevel gear 20, and the rotational speed is transmitted to the main drive shaft 5 via the output bevel gear 2. The integrated input is accelerated and split by the intermediate speed reducer 11. The power is transmitted to the three- stage speed reducers 6 and 19 at the left end and the right end through the left wing transmission shafts 38 and 39 respectively. The left three-stage speed reducer 6 adopts a driven spiral bevel gear I7 to reduce the output of the near end. The right three-stage speed reducer 19 adopts a driven spiral bevel gear II 18 to reduce the output of the far end. The left and right reducers are in the structure of axial line intersection angle spiral bevel gear reducer.
The left and right tilting structures 9 and 16 are mounted on the left and right wing brackets. The tilting structure adopts a planetary roller screw 23 to drive a hinge four-bar mechanism with composite rocker arms 21 and 25, so that the tilting control of the whole rotor nacelle is realized. The servo motor 17 drives the planetary screw 23 to rotate, the nut 20 on the upper part of the screw is pushed to drive the two auxiliary rocker arms 21 and 25 hinged with the nut to move, one auxiliary rocker arm 21 is hinged with the wing structure, and the other auxiliary rocker arm 25 is hinged with the reducer casing of the rotor, so that the reducer of the rotor is pushed to rotate around the tilting shaft.
In the tilting structure of the embodiment, the nacelle auxiliary rocker arm 33 and the wing side auxiliary rocker arm 29 which are hinged with the planetary screw nut 28 move, so that the secondary speed reducer casing of the rotor is pushed to rotate around the tilting shaft, and tilting control is realized. The tilting structure realizes a larger tilting angle range of the rotor wing in a limited space, and has the characteristics of small volume and light weight.
The servo motor is internally provided with an electromagnetic brake device, the trunnion connecting block 27 is provided with a photoelectric sensor 35, the planetary screw nut 28 is used as a reflecting surface of the photoelectric sensor, a theoretical movement track and a theoretical speed curve of the planetary screw nut 28 are arranged in the control system, the distance fed back by the photoelectric sensor 35 is converted into a speed in the working process of the tilting structure and then is transmitted to the control system, and the control system sends an instruction to the electromagnetic brake device to carry out power-on or power-off operation so as to realize the position maintenance of the tilting structure. And a limit groove is formed in the end face of the wing bracket and is matched with a limit pin on the auxiliary rocker 29 on the wing side of the tilting structure to limit the maximum tilting position of the tilting structure.
In this embodiment, a fairing is further disposed between the wing and the nacelle. When the mechanism moves at the position of 0 degrees to-5 degrees, the whole tilting structure can be ensured to be retracted in the fairing of the joint surface of the nacelle and the wing.
Claims (7)
1. A transmission mechanism for a wing of a tiltrotor aircraft, wherein the wing is respectively arranged at the left side and the right side of the body of the tiltrotor aircraft; a rotor nacelle is arranged at the tip of the wing; the machine body is fixed with a tilting shaft; the tilting shaft is used as a rotating shaft of the rotor nacelle, bears the load generated by the rotor nacelle and transmits the load to the fuselage; the rotor wing nacelle is responsible for tilting, and the rotor wing is arranged on the rotor wing nacelle and rotates along with the rotor wing nacelle to realize the conversion of flight modes; the method is characterized in that: the device comprises a main transmission shaft (5), a middle speed reducer (11), a left tilting structure (9), a right tilting structure (16), a left wing transmission shaft (38), a right wing transmission shaft (39), a left three-stage speed reducer (6) and a right three-stage speed reducer (19);
the output power of the main transmission shaft (5) is respectively transmitted to a left wing transmission shaft (38) and a right wing transmission shaft (39) after being accelerated and split by the intermediate speed reducer (11); the output end of the left wing transmission shaft (38) is provided with a left three-stage speed reducer (6); the output end of the right wing transmission shaft (39) is provided with a right three-stage speed reducer (19); the left three-stage speed reducer (6) and the right three-stage speed reducer (19) are arranged in the corresponding rotor nacelle;
the left tilting structure (9) and the right tilting structure (16) are arranged between the corresponding wing and the rotor nacelle; the left tilting structure (9) and the right tilting structure (16) are identical in structure; the left tilting structure (9) comprises a servo motor (25), a nacelle auxiliary rocker arm (29), a wing side auxiliary rocker arm (33), a planetary roller screw, a flange connecting block (26), a trunnion connecting block (27) and a tapered roller bearing (34); the planetary roller screw comprises a planetary screw nut (28) and a planetary screw (31); one end of the nacelle auxiliary rocker arm (29) is hinged with a case of the left three-stage speed reducer (6), and the other end of the nacelle auxiliary rocker arm is hinged with a planetary screw nut (28); one end of the wing side auxiliary rocker arm (33) is hinged with the wing structure, and the other end of the wing side auxiliary rocker arm is hinged with the planetary screw nut (28); the servo motor (25) drives the planetary screw rod (31) to rotate, and the planetary screw rod nut (28) at the upper part of the screw rod is pushed to drive the nacelle auxiliary rocker arm (29) and the wing side auxiliary rocker arm (33) to move, so that the left three-stage speed reducer (6) is pushed to rotate around the tilting shaft, and the tilting control of the rotor nacelle is realized;
the servo motor (25) is provided with an electromagnetic braking device; a photoelectric sensor (35) is arranged on the trunnion connecting block (27); the planetary screw nut (28) is used as a reflecting surface of the photoelectric sensor (35), and the motion track and the speed curve of the planetary screw nut (28) can be fed back in the control system; in the working process of the tilting structure, the distance fed back by the photoelectric sensor (35) is converted into speed and then is transmitted to the control system, and the control system compares the speed curves of the analysis theory and the actual planetary screw nut (28); when the speed curve exceeds a preset threshold, the control system sends a command to the electromagnetic braking device to conduct power-on or power-off operation, and the electromagnetic braking device conducts braking release or braking operation on the servo motor (25).
2. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: the engine also comprises a left engine (1), a right engine (22), a left-stage speed reducer (23) and a right-stage speed reducer (24); the output rotating speed of the left engine (1) is transmitted to the main transmission shaft (5) through a left primary speed reducer (23), and the output rotating speed of the right engine (22) is transmitted to the main transmission shaft (5) through a right primary speed reducer (24).
3. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: the end face of the wing structure is provided with a limit groove; and limiting pins are arranged on one sides of the nacelle auxiliary rocker arm (29) and the wing side auxiliary rocker arm (33) facing the wing structure, and the maximum tilting position of the tilting structure is limited through the cooperation of the limiting grooves and the limiting pins.
4. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: the left three-stage speed reducer (6) adopts a first-stage spiral bevel gear to reduce the output of the near end; the right three-stage speed reducer (19) adopts a first-stage spiral bevel gear to reduce the speed of the far-end output.
5. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: the left three-stage speed reducer (6) and the right three-stage speed reducer (19) are both in the form of axial line intersection angle spiral bevel gear speed reducer structures.
6. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: the tilting shaft is hollow, and wire equipment is arranged inside the tilting shaft.
7. A transmission for a tiltrotor aircraft wing according to claim 1, wherein: and a fairing is further arranged between the wing and the rotor nacelle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110510359.3A CN113232852B (en) | 2021-05-11 | 2021-05-11 | Transmission mechanism for tilting rotorcraft wing |
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| CN202110510359.3A CN113232852B (en) | 2021-05-11 | 2021-05-11 | Transmission mechanism for tilting rotorcraft wing |
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| CN113232852B true CN113232852B (en) | 2023-05-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113911378B (en) * | 2021-11-23 | 2022-11-01 | 南京航空航天大学 | Transmission mechanism of longitudinal tilt rotorcraft |
| CN115123537A (en) * | 2022-06-06 | 2022-09-30 | 重庆大学 | Tiltrotor mechanism and rotorcraft |
| CN115771614B (en) * | 2023-02-14 | 2023-06-13 | 江苏新扬新材料股份有限公司 | Large-scale gyroplane transmission system that verts |
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